EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 200,000 Max Cl/Cd: 62.99 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2010-il-200000-n5.txt Download as CSV file: xf-eh2010-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5584 0.08638 0.08308 -0.0056 1.0000 0.0131
-9.250 -0.5658 0.08065 0.07740 -0.0093 1.0000 0.0130
-9.000 -0.5794 0.07373 0.07054 -0.0152 1.0000 0.0129
-8.750 -0.5942 0.06820 0.06500 -0.0188 1.0000 0.0125
-8.500 -0.6122 0.06200 0.05872 -0.0203 1.0000 0.0126
-8.250 -0.6241 0.05545 0.05200 -0.0211 1.0000 0.0124
-8.000 -0.6362 0.04751 0.04374 -0.0208 1.0000 0.0125
-7.750 -0.6452 0.03963 0.03534 -0.0190 1.0000 0.0127
-7.500 -0.6428 0.03420 0.02927 -0.0169 1.0000 0.0137
-7.250 -0.6317 0.03079 0.02531 -0.0151 1.0000 0.0142
-7.000 -0.6199 0.02733 0.02135 -0.0132 1.0000 0.0145
-6.750 -0.6039 0.02472 0.01839 -0.0117 1.0000 0.0150
-6.500 -0.5845 0.02306 0.01651 -0.0105 1.0000 0.0156
-6.250 -0.5638 0.02172 0.01499 -0.0094 1.0000 0.0164
-6.000 -0.5427 0.02045 0.01353 -0.0082 1.0000 0.0174
-5.750 -0.5215 0.01925 0.01216 -0.0070 1.0000 0.0185
-5.500 -0.4858 0.01810 0.01079 -0.0087 0.9783 0.0206
-5.250 -0.4511 0.01694 0.00951 -0.0104 0.9516 0.0236
-5.000 -0.4157 0.01613 0.00859 -0.0120 0.9226 0.0265
-4.750 -0.3840 0.01548 0.00776 -0.0126 0.8913 0.0298
-4.500 -0.3576 0.01482 0.00702 -0.0122 0.8602 0.0344
-4.250 -0.3326 0.01437 0.00642 -0.0113 0.8315 0.0388
-4.000 -0.3088 0.01393 0.00584 -0.0103 0.8055 0.0450
-3.750 -0.2846 0.01360 0.00537 -0.0094 0.7820 0.0528
-3.500 -0.2606 0.01323 0.00493 -0.0085 0.7603 0.0626
-3.250 -0.2361 0.01295 0.00457 -0.0077 0.7402 0.0754
-3.000 -0.2112 0.01270 0.00426 -0.0070 0.7214 0.0927
-2.750 -0.1865 0.01243 0.00396 -0.0064 0.7038 0.1143
-2.500 -0.1618 0.01215 0.00370 -0.0058 0.6875 0.1442
-2.250 -0.1374 0.01182 0.00345 -0.0051 0.6718 0.1886
-2.000 -0.1138 0.01139 0.00321 -0.0045 0.6570 0.2582
-1.750 -0.0952 0.01047 0.00293 -0.0030 0.6435 0.4402
-1.250 -0.0571 0.00938 0.00305 0.0018 0.6179 0.8014
-1.000 -0.0300 0.00945 0.00312 0.0027 0.6050 0.8534
-0.750 -0.0013 0.00957 0.00316 0.0032 0.5925 0.8857
-0.500 0.0301 0.00972 0.00321 0.0030 0.5801 0.9087
-0.250 0.0628 0.00989 0.00326 0.0026 0.5680 0.9276
0.000 0.1042 0.01012 0.00336 0.0003 0.5556 0.9442
0.250 0.1452 0.01030 0.00341 -0.0021 0.5432 0.9560
0.500 0.1820 0.01037 0.00335 -0.0039 0.5318 0.9595
0.750 0.2149 0.01041 0.00330 -0.0051 0.5204 0.9637
1.000 0.2445 0.01047 0.00327 -0.0055 0.5097 0.9690
1.250 0.2795 0.01052 0.00323 -0.0071 0.4989 0.9718
1.500 0.3129 0.01058 0.00321 -0.0084 0.4885 0.9754
1.750 0.3445 0.01064 0.00322 -0.0093 0.4781 0.9798
2.000 0.3768 0.01070 0.00323 -0.0104 0.4677 0.9835
2.250 0.4106 0.01076 0.00323 -0.0118 0.4577 0.9867
2.750 0.4755 0.01091 0.00333 -0.0141 0.4377 0.9941
3.000 0.5089 0.01098 0.00337 -0.0155 0.4277 0.9974
3.250 0.5398 0.01108 0.00346 -0.0164 0.4185 1.0000
3.500 0.5626 0.01118 0.00356 -0.0155 0.4092 1.0000
3.750 0.5854 0.01130 0.00368 -0.0147 0.4006 1.0000
4.000 0.6079 0.01144 0.00380 -0.0138 0.3922 1.0000
4.250 0.6308 0.01157 0.00396 -0.0129 0.3831 1.0000
4.500 0.6535 0.01173 0.00415 -0.0121 0.3747 1.0000
4.750 0.6761 0.01190 0.00433 -0.0112 0.3656 1.0000
5.000 0.6990 0.01207 0.00455 -0.0103 0.3566 1.0000
5.250 0.7216 0.01227 0.00476 -0.0094 0.3480 1.0000
5.500 0.7444 0.01247 0.00502 -0.0085 0.3386 1.0000
5.750 0.7672 0.01268 0.00528 -0.0077 0.3293 1.0000
6.000 0.7899 0.01292 0.00555 -0.0068 0.3197 1.0000
6.250 0.8125 0.01316 0.00584 -0.0060 0.3098 1.0000
6.500 0.8354 0.01341 0.00616 -0.0051 0.2991 1.0000
6.750 0.8580 0.01368 0.00648 -0.0043 0.2876 1.0000
7.000 0.8800 0.01397 0.00684 -0.0034 0.2717 1.0000
7.250 0.9014 0.01433 0.00718 -0.0024 0.2518 1.0000
7.500 0.9225 0.01474 0.00757 -0.0015 0.2275 1.0000
7.750 0.9425 0.01527 0.00803 -0.0005 0.1989 1.0000
8.000 0.9613 0.01596 0.00859 0.0006 0.1629 1.0000
8.250 0.9772 0.01698 0.00938 0.0019 0.1178 1.0000
8.500 0.9902 0.01831 0.01046 0.0035 0.0701 1.0000
8.750 1.0017 0.01978 0.01171 0.0052 0.0368 1.0000
9.000 1.0145 0.02105 0.01293 0.0069 0.0239 1.0000
9.250 1.0281 0.02218 0.01416 0.0084 0.0187 1.0000
9.500 1.0399 0.02340 0.01549 0.0102 0.0153 1.0000
9.750 1.0525 0.02445 0.01666 0.0117 0.0131 1.0000
10.000 1.0601 0.02579 0.01812 0.0137 0.0116 1.0000
10.250 1.0593 0.02746 0.01991 0.0165 0.0109 1.0000
10.500 1.0608 0.02886 0.02144 0.0189 0.0105 1.0000
10.750 1.0605 0.03059 0.02332 0.0207 0.0100 1.0000
11.000 1.0592 0.03272 0.02559 0.0218 0.0095 1.0000
11.250 1.0579 0.03512 0.02816 0.0222 0.0092 1.0000
11.500 1.0569 0.03773 0.03089 0.0223 0.0089 1.0000
11.750 1.0560 0.04049 0.03377 0.0220 0.0087 1.0000
12.000 1.0542 0.04348 0.03687 0.0217 0.0085 1.0000
12.250 1.0530 0.04648 0.03998 0.0212 0.0083 1.0000
12.500 1.0518 0.04956 0.04317 0.0206 0.0081 1.0000
12.750 1.0496 0.05282 0.04653 0.0199 0.0079 1.0000
13.000 1.0478 0.05609 0.04991 0.0192 0.0078 1.0000
13.250 1.0452 0.05954 0.05346 0.0182 0.0076 1.0000
13.500 1.0426 0.06305 0.05708 0.0173 0.0075 1.0000
13.750 1.0408 0.06652 0.06068 0.0163 0.0075 1.0000
14.000 1.0352 0.07059 0.06485 0.0150 0.0072 1.0000
14.250 1.0312 0.07461 0.06900 0.0137 0.0072 1.0000
14.500 1.0230 0.07949 0.07401 0.0117 0.0069 1.0000
14.750 1.0177 0.08414 0.07883 0.0096 0.0068 1.0000
15.000 1.0108 0.08925 0.08411 0.0071 0.0068 1.0000
15.250 1.0040 0.09468 0.08972 0.0039 0.0065 1.0000
15.500 0.9947 0.10053 0.09572 0.0011 0.0065 1.0000
15.750 0.9851 0.10672 0.10206 -0.0022 0.0065 1.0000
16.000 0.9745 0.11351 0.10903 -0.0062 0.0062 1.0000
16.250 0.9630 0.12054 0.11621 -0.0100 0.0063 1.0000
16.500 0.9512 0.12785 0.12366 -0.0141 0.0064 1.0000
16.750 0.9380 0.13600 0.13196 -0.0189 0.0063 1.0000
17.000 0.9250 0.14430 0.14037 -0.0235 0.0065 1.0000
17.250 0.9106 0.15337 0.14956 -0.0286 0.0066 1.0000
17.500 0.8963 0.16277 0.15903 -0.0337 0.0069 1.0000
17.750 0.8813 0.17324 0.16957 -0.0393 0.0070 1.0000
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Polar data table (+)
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